Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

GOE 445 AIRFOIL (goe445-il)

GOE 445 AIRFOIL - Gottingen 445 airfoil


Airfoil goe445-il
Details Dat file Parser  
(goe445-il) GOE 445 AIRFOIL
Gottingen 445 airfoil
Max thickness 6.4% at 40% chord.
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
GOE 445 AIRFOIL
       17.       17.

 0.0000000 0.0000000
 0.0125000 0.0070000
 0.0250000 0.0105000
 0.0500000 0.0155000
 0.0750000 0.0190000
 0.1000000 0.0220000
 0.1500000 0.0265000
 0.2000000 0.0290000
 0.3000000 0.0315000
 0.4000000 0.0320000
 0.5000000 0.0295000
 0.6000000 0.0255000
 0.7000000 0.0210000
 0.8000000 0.0150000
 0.9000000 0.0083000
 0.9500000 0.0045000
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0125000 -.0070000
 0.0250000 -.0105000
 0.0500000 -.0155000
 0.0750000 -.0190000
 0.1000000 -.0220000
 0.1500000 -.0265000
 0.2000000 -.0290000
 0.3000000 -.0315000
 0.4000000 -.0320000
 0.5000000 -.0295000
 0.6000000 -.0255000
 0.7000000 -.0210000
 0.8000000 -.0150000
 0.9000000 -.0083000
 0.9500000 -.0045000
 1.0000000 0.0000000
No parser warnings Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file

Similar airfoils

HQ 0/7 AIRFOILPreviewDetails
NACA-M1 AIRFOILPreviewDetails
EPPLER EA 8(-1)-006 AIRFOILPreviewDetails
NACA 0006PreviewDetails
NACA 16-006PreviewDetails
NACA 64-008A AIRFOILPreviewDetails
NACA 0008-34PreviewDetails
GOE 444 AIRFOILPreviewDetails
LWK 80-080PreviewDetails
RAF 30 MOD AIRFOILPreviewDetails

Polars for GOE 445 AIRFOIL (goe445-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   goe445-il50,000918.4 at α=3.75°Mach=0 Ncrit=9Xfoil predictionDetails
   goe445-il50,000519.1 at α=3°Mach=0 Ncrit=5Xfoil predictionDetails
   goe445-il100,000924.2 at α=3°Mach=0 Ncrit=9Xfoil predictionDetails
   goe445-il100,000530.8 at α=2.5°Mach=0 Ncrit=5Xfoil predictionDetails
   goe445-il200,000942.4 at α=2.25°Mach=0 Ncrit=9Xfoil predictionDetails
   goe445-il200,000539 at α=2°Mach=0 Ncrit=5Xfoil predictionDetails
   goe445-il500,000949.1 at α=1.5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe445-il500,000538 at α=3.25°Mach=0 Ncrit=5Xfoil predictionDetails
   goe445-il1,000,000946.4 at α=3.25°Mach=0 Ncrit=9Xfoil predictionDetails
   goe445-il1,000,000542.2 at α=3.25°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit